| acceleration(SpacecraftState, double[]) |  | 0% | | n/a | 1 | 1 | 3 | 3 | 1 | 1 |
| acceleration(FieldSpacecraftState, CalculusFieldElement[]) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| NewtonianAttraction(double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getMu(Field) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| addContribution(FieldSpacecraftState, FieldTimeDerivativesEquations) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| addContribution(SpacecraftState, TimeDerivativesEquations) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMu() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| dependsOnPositionOnly() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFieldEventsDetectors(Field) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |